CN112067081A - Method for monitoring additional parameters before launching of carrier rocket - Google Patents
Method for monitoring additional parameters before launching of carrier rocket Download PDFInfo
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- CN112067081A CN112067081A CN202010676885.2A CN202010676885A CN112067081A CN 112067081 A CN112067081 A CN 112067081A CN 202010676885 A CN202010676885 A CN 202010676885A CN 112067081 A CN112067081 A CN 112067081A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
- G01F23/00—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm
- G01F23/22—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water
- G01F23/26—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water by measuring variations of capacity or inductance of capacitors or inductors arising from the presence of liquid or fluent solid material in the electric or electromagnetic fields
- G01F23/263—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water by measuring variations of capacity or inductance of capacitors or inductors arising from the presence of liquid or fluent solid material in the electric or electromagnetic fields by measuring variations in capacitance of capacitors
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
- G01F23/00—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm
- G01F23/22—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water
- G01F23/26—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water by measuring variations of capacity or inductance of capacitors or inductors arising from the presence of liquid or fluent solid material in the electric or electromagnetic fields
- G01F23/263—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water by measuring variations of capacity or inductance of capacitors or inductors arising from the presence of liquid or fluent solid material in the electric or electromagnetic fields by measuring variations in capacitance of capacitors
- G01F23/265—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water by measuring variations of capacity or inductance of capacitors or inductors arising from the presence of liquid or fluent solid material in the electric or electromagnetic fields by measuring variations in capacitance of capacitors for discrete levels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K7/00—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements
- G01K7/16—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using resistive elements
- G01K7/18—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using resistive elements the element being a linear resistance, e.g. platinum resistance thermometer
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- Measurement Of Levels Of Liquids Or Fluent Solid Materials (AREA)
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Abstract
The invention relates to a carrier rocket pre-shooting additional parameter monitoring system.A ground power supply module controls a liquid level sensor on an arrow, a liquid level converter on the arrow, a temperature sensor on the arrow and a temperature and humidity sensor on the arrow to supply power; the rocket liquid level sensor and the rocket liquid level converter jointly act to output a voltage value V representing the liquid level height information of the propellantiAnd applying the voltage value ViTransmitted to a ground liquid level signal processing module, and the ground liquid level signal processing module processes the voltage value V according toiAnd determining the liquid level of the propellant on the rocket and transmitting the liquid level to the ground communication module. The invention can meet the requirement of continuous monitoring of temperature and humidity measuring points in the fairing, also meets the requirement of accurate measurement of the liquid level of the low-temperature propellant, can effectively measure other temperature parameters on an arrow transmitted in a long distance, has higher reliability and simultaneouslyGround equipment and a ground cable network can be reused, so that the cost is saved, and the economical efficiency is better.
Description
Technical Field
The invention relates to a method for monitoring additional parameters before launching of a carrier rocket, and belongs to the technical field of aerospace measurement.
Background
The parameters of the carrier rocket before launching and the parameters of the carrier rocket in flight are mostly measured by an on-rocket measuring system, the parameters are numerous and complex in variety, generally, each cabin section is provided with an independent acquisition and editing system to acquire and edit the parameters nearby, the acquisition and editing system consists of a current conversion adapter and a data acquisition and editing device, and a power supply and distribution time sequence system is used for completing the unified power supply of a single machine of the measuring system.
After the carrier rocket, particularly a new generation of low-temperature carrier rocket, is transferred to a launching site, the temperature and humidity parameters in the fairing need to be continuously monitored, and parameters related to filling are monitored, but the low-temperature propellant has a natural phenomenon of volatilization after filling is completed, and the propellant needs to be replenished in real time according to a monitoring result, so that the filling process is long in time, and the filling process needs to be monitored all the time. Under the existing measurement mode, if a transmission mode of radio frequency measurement is adopted, the requirement of long-term (generally, the continuous time can not exceed 4 hours) power-on can not be completed.
Disclosure of Invention
The technical problem solved by the invention is as follows: the method overcomes the defects of the prior art, and provides a carrier rocket pre-injection additional parameter monitoring method to complete long-term monitoring of pre-injection parameters, so that confirmation of a pre-injection filling process and a fairing temperature and humidity state is realized.
The technical scheme of the invention is as follows:
a carrier rocket pre-shooting additional parameter monitoring system comprises an on-rocket liquid level sensor, an on-rocket liquid level converter, an on-rocket temperature sensor, an on-rocket temperature and humidity sensor, a ground liquid level signal processing module, a ground temperature and humidity signal processing module, a ground power supply module and a ground communication module;
the ground power supply module controls the on-arrow liquid level sensor, the on-arrow liquid level converter, the on-arrow temperature sensor and the on-arrow temperature and humidity sensor to supply power;
the rocket liquid level sensor and the rocket liquid level converter jointly act to output a voltage value V representing the liquid level height information of the propellantiAnd applying the voltage value ViTransmitted to a ground liquid level signal processing module, and the ground liquid level signal processing module processes the voltage value V according toiDetermining the liquid level height of the propellant on the rocket and transmitting the liquid level height to a ground communication module;
the rocket-mounted temperature sensor is a four-wire platinum resistance temperature sensor, collects temperature information represented by resistance in the propellant filling process, and transmits the temperature information to the ground temperature signal processing module, the ground temperature signal processing module is a constant current source temperature converter, the temperature information output by the rocket-mounted temperature sensor is uniformly converted, 0-5V voltage signals are output, and the ground signal processing module converts the received 0-5V voltage signals into actual rocket-mounted temperature information and transmits the actual rocket-mounted temperature information to the ground communication module;
the on-arrow temperature and humidity sensor collects temperature and humidity digital signals in the fairing and transmits the temperature and humidity digital signals to the ground temperature and humidity signal processing module, and the ground temperature and humidity signal processing module converts the received temperature and humidity digital signals into analog signals, then restores the analog signals into on-arrow fairing temperature and humidity information and transmits the temperature and humidity information to the ground communication module;
and the ground communication module transmits the received rocket propellant liquid level height information, the rocket actual temperature information and the rocket fairing temperature and humidity information to a ground side launch control system, and the ground side launch control system interprets the information and confirms the states of the pre-injection filling process and the fairing temperature and humidity conditions.
Further, the method for determining the liquid level height of the propellant on the arrow comprises the following steps:
when the liquid level of the propellant is at the odd number section of the liquid level sensor, the liquid level height of the propellant on the arrow
When the liquid level of the propellant is at the even number section of the liquid level sensor, the liquid level height of the propellant on the rocket
Wherein L1 is the length of the first section of the liquid level sensor, L2 is the length of the nth section of the liquid level sensor, and n is an integer greater than 1; u shapeminIs a triangular wave zero voltage, UmaxIs a full-scale voltage of the triangular wave.
Further, the method for uniformly converting the temperature information output by the temperature sensor on the arrow comprises the following steps: after a 1mA constant current is adopted to pass through the platinum resistor, the voltage at two ends of the platinum resistor is directly intercepted, and a 0-5V voltage signal is output after filtering and amplification.
Furthermore, the on-arrow liquid level sensor is a capacitive liquid level sensor, a point type filling liquid level sensor is adopted for liquid level filling measurement of the on-arrow kerosene tank, and the point type filling liquid level sensor and a continuous type filling liquid level sensor are adopted for liquid level filling measurement of the on-arrow oxygen tank at the same time.
Further, the point type liquid level sensor is a ring-shaped capacitor composed of an inner ring and an outer ring, when liquid flows between the inner ring and the outer ring, the dielectric constant is changed, the changed capacitance is input into the converter, and when the capacitance change of the sensor exceeds the fixed capacitance of an inner bridge of the converter, the converter sends out a passive contact signal.
Furthermore, the sensitive capacitance part of the continuous liquid level sensor consists of an inner electrode and four outer electrodes, wherein the outer electrodes are sequentially divided into an odd capacitance group and an even capacitance group, when liquid flows between the inner electrode and the outer electrode through the flow guide pipe, the dielectric constant is changed, and the changed capacitance is input into the converter.
Furthermore, when the outer electrodes of the odd and even groups of the sensor are alternately immersed by liquid, two groups of capacitors output by the sensor correspondingly alternate, and the change of the liquid level height is finally reflected as the change of the capacitance of the sensor.
Furthermore, the ground liquid level signal processing module converts a non-electrical contact signal output by the point type liquid level sensor, a triangular wave output by the continuous liquid level converter and a continuous voltage signal into digital quantity.
Further, the method for converting the triangular wave and continuous voltage signals output by the converter into digital quantity by the continuous liquid level signals comprises the following steps:
(1) performing linear fitting according to the linear wave output, and judging whether the liquid level rises or falls according to the linear slope;
(2) according to a linear fitting equation, the current voltage is estimated by combining the linear voltage obtained by collection, and the number of sections of the liquid level is preliminarily judged;
(3) calculating the liquid level height in the initial state according to the linear wave voltage;
(4) and obtaining the liquid level height by utilizing the triangular wave voltage value and the section number of the liquid level.
A method for monitoring additional parameters before launching of a carrier rocket comprises the following steps:
s1, the ground power supply module controls the power supply of the on-arrow liquid level sensor, the on-arrow liquid level converter, the on-arrow temperature sensor and the on-arrow temperature and humidity sensor;
s2, the rocket liquid level sensor and the rocket liquid level converter act together to output a voltage value V representing the liquid level height information of the propellantiAnd applying the voltage value ViTransmitted to a ground liquid level signal processing module, and the ground liquid level signal processing module processes the voltage value V according toiDetermining the liquid level height of the propellant on the rocket and transmitting the liquid level height to a ground communication module;
s3, acquiring temperature information represented by a resistor in the propellant filling process by a four-wire platinum resistor temperature sensor on the rocket, transmitting the temperature information to a ground temperature signal processing module, uniformly converting the temperature information output by the temperature sensor on the rocket by the ground temperature signal processing module, outputting a 0-5V voltage signal, converting the received 0-5V voltage signal into actual temperature information on the rocket by the ground signal processing module, and transmitting the actual temperature information to a ground communication module;
s4, the on-arrow temperature and humidity sensor collects temperature and humidity digital signals in the fairing and transmits the temperature and humidity digital signals to the ground temperature and humidity signal processing module, and the ground temperature and humidity signal processing module converts the received temperature and humidity digital signals into analog signals, then restores the analog signals into on-arrow fairing temperature and humidity information and transmits the temperature and humidity information to the ground communication module;
and S5, the ground communication module transmits the received rocket propellant liquid level height information, the rocket actual temperature information and the rocket fairing temperature and humidity information to the ground side launch control system, and the ground side launch control system interprets the information and confirms the states of the pre-injection filling process and the fairing temperature and humidity conditions.
Compared with the prior art, the invention has the beneficial effects that:
(1) according to the invention, the sensor and the converter of the measuring point are directly led to the ground through the arrow ground cable, so that the transmission channel is efficient and simple, the problem of communication delay caused by the conventional communication modes such as a network and a serial port is effectively avoided, and the monitoring of the measured temperature, humidity and filling related parameters is more accurate;
(2) according to the invention, the measurement of the temperature and humidity parameters is carried out by adopting a measurement mode, so that the humidity measurement error can be controlled to be +/-2.5% RH, the standard is better than the general requirement index +/-4% RH, the filling liquid level measurement error is less than +/-2 mm, and the precision is higher;
(3) the system can meet the requirement of continuous monitoring of temperature and humidity measuring points in the fairing, also meets the requirement of accurate measurement of the liquid level of the low-temperature propellant, can effectively measure other temperature parameters on the arrow transmitted in a long distance, has higher reliability, can be repeatedly used by ground equipment and a ground cable network, saves cost and has better economy;
(4) the invention adopts a mode of independently outputting the parameters to be monitored out of the measuring system, thereby simplifying the working process of the shooting range and optimizing the personnel post.
Drawings
FIG. 1 is a temperature and humidity parameter testing system of the present invention;
FIG. 2 is a schematic diagram of the fill level measurement of the present invention;
FIG. 3 is a schematic diagram of a single-circuit temperature converter of the present invention.
Detailed Description
The invention is further illustrated by the following examples.
A carrier rocket pre-shooting additional parameter monitoring system comprises an on-rocket liquid level sensor, an on-rocket liquid level converter, an on-rocket temperature sensor, an on-rocket temperature and humidity sensor, a ground liquid level signal processing module, a ground temperature and humidity signal processing module, a ground power supply module and a ground communication module;
the ground power supply module controls the on-arrow liquid level sensor, the on-arrow liquid level converter, the on-arrow temperature sensor and the on-arrow temperature and humidity sensor to supply power;
the rocket liquid level sensor and the rocket liquid level converter jointly act to output a voltage value V representing the liquid level height information of the propellantiAnd applying the voltage value ViTransmitted to a ground liquid level signal processing module, and the ground liquid level signal processing module processes the voltage value V according toiDetermining the liquid level height of the propellant on the rocket and transmitting the liquid level height to a ground communication module;
the rocket-mounted temperature sensor is a four-wire platinum resistance temperature sensor, collects temperature information represented by resistance in the propellant filling process, and transmits the temperature information to the ground temperature signal processing module, the ground temperature signal processing module is a constant current source temperature converter, the temperature information output by the rocket-mounted temperature sensor is uniformly converted, 0-5V voltage signals are output, and the ground signal processing module converts the received 0-5V voltage signals into actual rocket-mounted temperature information and transmits the actual rocket-mounted temperature information to the ground communication module;
the on-arrow temperature and humidity sensor collects temperature and humidity digital signals in the fairing and transmits the temperature and humidity digital signals to the ground temperature and humidity signal processing module, and the ground temperature and humidity signal processing module converts the received temperature and humidity digital signals into analog signals, then restores the analog signals into on-arrow fairing temperature and humidity information and transmits the temperature and humidity information to the ground communication module;
and the ground communication module transmits the received rocket propellant liquid level height information, the rocket actual temperature information and the rocket fairing temperature and humidity information to a ground side launch control system, and the ground side launch control system interprets the information and confirms the states of the pre-injection filling process and the fairing temperature and humidity conditions.
The method for determining the liquid level height of the propellant on the arrow comprises the following steps: when the liquid level of the propellant is at the odd number section of the liquid level sensor, the liquid level height of the propellant on the arrow
When the liquid level of the propellant is at the even number section of the liquid level sensor, the liquid level height of the propellant on the rocket
Wherein L1 is the length of the first section of the liquid level sensor, L2 is the length of the nth section of the liquid level sensor, and n is an integer greater than 1; u shapeminIs a triangular wave zero voltage, UmaxIs a full-scale voltage of the triangular wave.
The method for uniformly converting the temperature information output by the temperature sensors on the arrow comprises the following steps: after a 1mA constant current is adopted to pass through the platinum resistor, the voltage at two ends of the platinum resistor is directly intercepted, and a 0-5V voltage signal is output after filtering and amplification.
The liquid level sensor on the arrow is a capacitance type liquid level sensor, the liquid level filling measurement of the coal oil tank on the arrow adopts a point type filling liquid level sensor, and the liquid level filling measurement of the oxygen tank on the arrow simultaneously adopts the point type filling liquid level sensor and a continuous type filling liquid level sensor.
The point level sensor is a ring capacitor consisting of an inner ring and an outer ring, which when the liquid flows between the inner and outer rings, causes a change in the dielectric constant, the changed capacitance is input to the transducer, and the transducer emits a passive contact signal when the change in the capacitance of the sensor exceeds the fixed capacitance of the bridge inside the transducer.
The sensitive capacitance part of the continuous liquid level sensor consists of an inner electrode and four outer electrodes, wherein the outer electrodes are sequentially divided into an odd capacitance group and an even capacitance group, when liquid flows between the inner electrode and the outer electrode through the flow guide pipe, the dielectric constant is changed, and the changed capacitance is input into the converter.
When the outer electrodes of the odd and even groups of the sensor are alternately immersed by liquid, two groups of capacitors output by the sensor correspondingly alternate, and the change of the liquid level height is finally reflected as the change of the capacitance of the sensor.
The ground liquid level signal processing module converts the non-electrical contact signal output by the point type liquid level sensor, the triangular wave output by the continuous liquid level converter and the continuous voltage signal into digital quantity. The method for converting the triangular wave and continuous voltage signals output by the converter into digital quantity by the continuous liquid level signals comprises the following steps:
(1) performing linear fitting according to the linear wave output, and judging whether the liquid level rises or falls according to the linear slope;
(2) according to a linear fitting equation, the current voltage is estimated by combining the linear voltage obtained by collection, and the number of sections of the liquid level is preliminarily judged;
(3) calculating the liquid level height in the initial state according to the linear wave voltage;
(4) and obtaining the liquid level height by utilizing the triangular wave voltage value and the section number of the liquid level.
A method for monitoring additional parameters before launching of a carrier rocket comprises the following steps:
s1, the ground power supply module controls the power supply of the on-arrow liquid level sensor, the on-arrow liquid level converter, the on-arrow temperature sensor and the on-arrow temperature and humidity sensor;
s2, the rocket liquid level sensor and the rocket liquid level converter act together to output a voltage value V representing the liquid level height information of the propellantiAnd applying the voltage value ViTransmitted to a ground liquid level signal processing module, and the ground liquid level signal processing module processes the voltage value V according toiDetermining the liquid level height of the propellant on the rocket and transmitting the liquid level height to a ground communication module;
s3, acquiring temperature information represented by a resistor in the propellant filling process by a four-wire platinum resistor temperature sensor on the rocket, transmitting the temperature information to a ground temperature signal processing module, uniformly converting the temperature information output by the temperature sensor on the rocket by the ground temperature signal processing module, outputting a 0-5V voltage signal, converting the received 0-5V voltage signal into actual temperature information on the rocket by the ground signal processing module, and transmitting the actual temperature information to a ground communication module;
s4, the on-arrow temperature and humidity sensor collects temperature and humidity digital signals in the fairing and transmits the temperature and humidity digital signals to the ground temperature and humidity signal processing module, and the ground temperature and humidity signal processing module converts the received temperature and humidity digital signals into analog signals, then restores the analog signals into on-arrow fairing temperature and humidity information and transmits the temperature and humidity information to the ground communication module;
and S5, the ground communication module transmits the received rocket propellant liquid level height information, the rocket actual temperature information and the rocket fairing temperature and humidity information to the ground side launch control system, and the ground side launch control system interprets the information and confirms the states of the pre-injection filling process and the fairing temperature and humidity conditions.
The principle and the using method of the system are briefly described by taking the temperature and humidity monitoring, the filling liquid level monitoring and part of temperature parameters of a certain rocket before additional shooting as an example.
Firstly, a temperature and humidity parameter system is shown in figure 1.
1. Selecting types of temperature and humidity sensors on arrows:
aiming at the measurement requirements of temperature and humidity, a sensor with the optimal performance is selected firstly, and the sensor passes through a HMP110 type temperature and humidity sensor of a more-selective Wisala company, and has the following advantages: inherent system measurement errors and long-line measurement errors of analog measurement can be avoided, the anti-interference capability of bus transmission is high, and external interference influence is effectively inhibited; the commercial bus type sensor is mature and reliable, is verified by commercial and industrial application, has obvious unit price advantage and meets the requirement of low-cost design of models. The performance parameters of the sensor are:
range: humidity: 0-100%, temperature: -40 to 80 ℃;
maximum allowed error: humidity + -2.5% RH, temperature + -0.4 deg.C;
input voltage: 5-28 VDC;
power consumption current: average 1mA, peak 5 mA;
protection rating: IP 65.
2. Measurement platform design
The measurement platform selects a portable computer to cooperate with a cRIO platform of NI company to carry out communication of measurement information and real-time display of measurement results, and selects an NI 9871 module to complete RS485 communication with the HMP110 and complete RS422 communication with an additional system comprehensive processing module.
The main indexes of the NI 9871 communication module are as follows:
4 RS485/RS422 communication interfaces;
a baud rate of 14 bits/s to 1.842 Mbit/s;
independent 64B UART FIFO buffer per channel;
data bits 5,6,7, 8; stop positions 1,1.5 and 2;
8V to 28VDC external supply;
the operating range is-40 ℃ to 70 ℃.
3. Power supply design
Newly-researched temperature and humidity measurement system needs power supply at three places, which are respectively as follows:
the on-arrow sensor HMP110 requires 5V to 28VDC for power supply;
a cRIO host, requiring 9V to 30VDC for power supply;
the NI 9871 communication module independently supplies power, and the power supply requires 8V-28 VDC;
according to the power supply requirement, two NI power supply modules NI PS-15 matched with the cDAQ host are selected to supply power to the sensors on the arrow and the ground equipment, and the power supply indexes of the NI PS-15 are as follows:
supply voltage: 24 VDC;
maximum supply current: 5A.
4. Design of interface with air conditioning system of full rocket transport vehicle
Because the output of the arrow sensor HMP110 is an RS485 digital signal, and the interface of the air-conditioning control system is a 0-5V analog signal, the temperature and humidity acquisition system needs to complete the function of converting the digital signal into the analog signal, and the part of the function is completed by the NI9264 board card.
And measuring the filling liquid level, which mainly comprises a filling liquid level sensor, a filling liquid level converter and filling liquid level ground equipment. The principle of the filling level parameter measurement is shown in figure 2:
1. rocket liquid level sensor and converter model selection
The liquid level of the coal oil tank is measured by a point type filling liquid level sensor, and the oxygen tank is measured by a point type filling liquid level sensor and a continuous type filling liquid level sensor at the same time, and the parameters to be measured are shown in table 1.
TABLE 1 fill level measurement parameters
The continuous type liquid level sensor and the point type liquid level sensor both adopt capacitance type liquid level sensors.
The point level sensor is a ring capacitor consisting of an inner ring and an outer ring, which when the liquid flows between the inner and outer rings, causes a change in the dielectric constant, the changing capacitance is input to the transducer, and the transducer emits a passive contact signal when the change in capacitance of the sensor exceeds the fixed capacitance of the bridge inside the transducer.
The sensitive capacitance part of the continuous liquid level sensor consists of an inner electrode and four outer electrodes, wherein the outer electrodes are sequentially divided into an odd capacitance group and an even capacitance group. When liquid flows between the inner electrode and the outer electrode through the flow guide pipe, the dielectric constant is changed, and the capacitance is changed and then is input into the converter. When the outer electrodes of the odd and even groups of the sensor are alternately immersed by liquid, two groups of capacitors output by the sensor are alternately changed, and the change of the liquid level height is finally reflected as the change of the capacitance of the sensor.
The filling liquid level ground equipment can convert a non-electrical contact signal output by the point type liquid level sensor, a triangular wave output by the continuous liquid level converter and a continuous voltage signal into digital quantity.
2. Power supply design
The DC28V power supply voltage required by the rocket-mounted liquid level converter is completed by liquid level ground processing equipment, the filling liquid level ground processing equipment is connected to the mains supply AC220V, is converted into DC28V by an internal AC/DC module, and is input to the rocket-mounted liquid level converter through a rocket-mounted cable, so that the power supply work is completed.
3. Fill level signal processing
The arrow point type filling liquid level converter outputs a non-electric contact signal, the continuous liquid level converter outputs a voltage signal, the liquid level ground processing equipment finishes acquisition of the output signal of the converter and converts the signal into a physical quantity through an internal integrated algorithm.
For the non-electric contact on-off signal output by the point type liquid level converter, the ground processing equipment completes data processing through a voltage division circuit, and determines whether the point type signal comes or not by utilizing different voltage output values in the opening state and the closing state of the switch.
For the continuous liquid level signal, the triangular wave signal and the linear wave signal output by the converter need to be comprehensively processed to obtain a liquid level value. The specific algorithm is as follows:
firstly, a linear fitting equation is carried out according to the linear wave output, and whether the liquid level rises or falls is judged according to the linear slope;
according to a linear fitting equation, by combining the acquired linear voltage, estimating the current voltage after eliminating a field value obtained by environmental factors such as liquid level shaking and boiling, and preliminarily judging the number of sections of the liquid level;
calculating the liquid level height in the initial state according to the linear wave voltage;
and obtaining the liquid level height by using the triangular wave voltage value and the section number of the liquid level.
The calculation process is described by taking the liquid level measurement range 1630mm, 6 sections in total, the length of the first section 270mm, and the length of each section 272mm of the second, third and fourth sections as an example.
When the liquid level is in the odd number section, the calculation method of the liquid level height is shown in the formula ()
When the liquid level is at the even number section, the calculation method of the liquid level height is shown in the formula (2)
Hx-tank level height (mm);
H0-height (mm) of tank zero to sensor zero;
vi-converter output triangular voltage (V);
Umin-triangular wave null voltage (V), Umin ═ 0.1V (empirical value);
Umax-the full-scale voltage (V) of the triangle wave, Umax ═ 4.7V (empirical value);
the parameters of the liquid level sensor are detailed in a product certificate.
Third, other temperature parameter monitoring
The measurement principle is shown in fig. 3.
The output of the temperature sensor on the arrow is a platinum resistance signal, the resistance value of a cable is superposed on the basis of the output resistance signal of the sensor by the collected signal due to the transmission resistance signal of a longer cable, so that a large measurement error is caused, a four-wire platinum resistance is adopted, the signal output by the platinum resistance sensor is uniformly converted by a four-wire constant current source temperature converter on the ground, the voltage at two ends of the platinum resistance is directly intercepted after the platinum resistance is passed by 1mA constant current, and 0-5V voltage signals are output after a filtering and amplifying circuit.
According to the invention, the sensor and the converter of the measuring point are directly led to the ground through the arrow ground cable, so that the transmission channel is efficient and simple, the problem of communication delay caused by the conventional communication modes such as a network and a serial port is effectively avoided, and the monitoring of the measured temperature, humidity and filling related parameters is more accurate;
according to the invention, the measurement of the temperature and humidity parameters is carried out by adopting a measurement mode, so that the humidity measurement error can be controlled to be +/-2.5% RH, the standard is better than the general requirement index +/-4% RH, the filling liquid level measurement error is less than +/-2 mm, and the precision is higher;
the invention can meet the requirement of continuous monitoring of temperature and humidity measuring points in the fairing, also meets the requirement of accurate measurement of the liquid level of the low-temperature propellant, can effectively measure other temperature parameters on the arrow transmitted in a long distance, has higher reliability, can be repeatedly used by ground equipment and a ground cable network, saves cost and has better economy.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. A carrier rocket pre-shooting additional parameter monitoring system is characterized by comprising an on-rocket liquid level sensor, an on-rocket liquid level converter, an on-rocket temperature sensor, an on-rocket temperature and humidity sensor, a ground liquid level signal processing module, a ground temperature and humidity signal processing module, a ground power supply module and a ground communication module;
the ground power supply module controls the on-arrow liquid level sensor, the on-arrow liquid level converter, the on-arrow temperature sensor and the on-arrow temperature and humidity sensor to supply power;
the rocket liquid level sensor and the rocket liquid level converter jointly act to output a voltage value V representing the liquid level height information of the propellantiAnd applying the voltage value ViTransmitted to a ground liquid level signal processing module, and the ground liquid level signal processing module processes the voltage value V according toiDetermining the liquid level height of the propellant on the rocket and transmitting the liquid level height to a ground communication module;
the rocket-mounted temperature sensor is a four-wire platinum resistance temperature sensor, collects temperature information represented by resistance in the propellant filling process, and transmits the temperature information to the ground temperature signal processing module, the ground temperature signal processing module is a constant current source temperature converter, the temperature information output by the rocket-mounted temperature sensor is uniformly converted, 0-5V voltage signals are output, and the ground signal processing module converts the received 0-5V voltage signals into actual rocket-mounted temperature information and transmits the actual rocket-mounted temperature information to the ground communication module;
the on-arrow temperature and humidity sensor collects temperature and humidity digital signals in the fairing and transmits the temperature and humidity digital signals to the ground temperature and humidity signal processing module, and the ground temperature and humidity signal processing module converts the received temperature and humidity digital signals into analog signals, then restores the analog signals into on-arrow fairing temperature and humidity information and transmits the temperature and humidity information to the ground communication module;
and the ground communication module transmits the received rocket propellant liquid level height information, the rocket actual temperature information and the rocket fairing temperature and humidity information to a ground side launch control system, and the ground side launch control system interprets the information and confirms the states of the pre-injection filling process and the fairing temperature and humidity conditions.
2. A vehicle rocket pre-launch additional parameter monitoring system as recited in claim 1, wherein the propellant level height on the rocket is determined by the method comprising:
when the liquid level of the propellant is at the odd number section of the liquid level sensor, the liquid level height of the propellant on the arrow
When the liquid level of the propellant is at the even number section of the liquid level sensor, the liquid level height of the propellant on the rocket
Wherein, L1 is the length of the first section of the liquid level sensor, L2 is the length of the nth section of the liquid level sensor, and n is more than1 is an integer; u shapeminIs a triangular wave zero voltage, UmaxIs a full-scale voltage of the triangular wave.
3. A carrier rocket pre-launch additional parameter monitoring system as recited in claim 1, wherein the method for uniformly transforming the temperature information output by the temperature sensors on the rocket comprises: after a 1mA constant current is adopted to pass through the platinum resistor, the voltage at two ends of the platinum resistor is directly intercepted, and a 0-5V voltage signal is output after filtering and amplification.
4. The system of claim 1, wherein the rocket-mounted level sensor is a capacitive level sensor, a point-type filling level sensor is used for rocket-mounted tank level filling measurement, and a point-type filling level sensor and a continuous filling level sensor are used for rocket-mounted tank level filling measurement.
5. A launch vehicle pre-launch supplemental parameter monitoring system according to claim 1 wherein the point level sensor is an annular capacitor comprising an inner ring and an outer ring, which when fluid flows between the inner and outer rings causes a change in the dielectric constant, the changed capacitance being fed to the transducer, the transducer emitting a passive contact signal when the change in capacitance of the sensor exceeds the fixed capacitance of the bridge within the transducer.
6. The system as set forth in claim 1, wherein the sensing capacitor of the continuous type liquid level sensor is composed of an inner electrode and four outer electrodes, wherein the outer electrodes are sequentially divided into odd number capacitor banks and even number capacitor banks, and when the liquid flows between the inner and outer electrodes through the flow guide tube, the dielectric constant is changed, so that the changed capacitance is inputted into the transducer.
7. The system of claim 6, wherein when the electrodes of the odd and even sets of sensors are alternately immersed in the liquid, the two sets of capacitors output by the sensors alternately change, and the change in the liquid level is finally reflected as a change in the capacitance of the sensors.
8. The system for monitoring the pre-launch additional parameters of a launch vehicle according to claim 4, wherein the ground level signal processing module converts the electrical contact-free signal output by the point-type level sensor, the triangular wave output by the continuous level transducer, and the continuous voltage signal into digital values.
9. The system of claim 8, wherein the continuous liquid level signal is converted into digital value from triangular wave and continuous voltage signals output by the converter by:
(1) performing linear fitting according to the linear wave output, and judging whether the liquid level rises or falls according to the linear slope;
(2) according to a linear fitting equation, the current voltage is estimated by combining the linear voltage obtained by collection, and the number of sections of the liquid level is preliminarily judged;
(3) calculating the liquid level height in the initial state according to the linear wave voltage;
(4) and obtaining the liquid level height by utilizing the triangular wave voltage value and the section number of the liquid level.
10. A method for monitoring additional parameters before launching of a carrier rocket is characterized by comprising the following steps:
s1, the ground power supply module controls the power supply of the on-arrow liquid level sensor, the on-arrow liquid level converter, the on-arrow temperature sensor and the on-arrow temperature and humidity sensor;
s2, the rocket liquid level sensor and the rocket liquid level converter act together to output a voltage value V representing the liquid level height information of the propellantiAnd applying the voltage value ViTransmitted to a ground liquid level signal processing module, and the ground liquid level signal processing module processes the voltage value V according toiDetermining the liquid level height of the propellant on the rocket and transmitting the liquid level height to a ground communication module;
s3, acquiring temperature information represented by a resistor in the propellant filling process by a four-wire platinum resistor temperature sensor on the rocket, transmitting the temperature information to a ground temperature signal processing module, uniformly converting the temperature information output by the temperature sensor on the rocket by the ground temperature signal processing module, outputting a 0-5V voltage signal, converting the received 0-5V voltage signal into actual temperature information on the rocket by the ground signal processing module, and transmitting the actual temperature information to a ground communication module;
s4, the on-arrow temperature and humidity sensor collects temperature and humidity digital signals in the fairing and transmits the temperature and humidity digital signals to the ground temperature and humidity signal processing module, and the ground temperature and humidity signal processing module converts the received temperature and humidity digital signals into analog signals, then restores the analog signals into on-arrow fairing temperature and humidity information and transmits the temperature and humidity information to the ground communication module;
and S5, the ground communication module transmits the received rocket propellant liquid level height information, the rocket actual temperature information and the rocket fairing temperature and humidity information to the ground side launch control system, and the ground side launch control system interprets the information and confirms the states of the pre-injection filling process and the fairing temperature and humidity conditions.
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